極超音速衝撃波干渉流れにおける空力加熱の数値解析

抄録

It is still challenging to predict surface heat-transfer rate in hypersonic flow computations. In this paper, we first performed numerical experiments by changing numerical flux functions and meshes for a hypersonic flow around a hemisphere. Results show that AUSM+ flux function by Liou (1996) on a carefully refined mesh can lead to a shock stable solution with an accurate aerodynamic heating on the surface. Then, a numerical simulation on a hypersonic flow around two bodies involving a shock/shock interaction and a boundary-layer separation has been conducted by using the same method. Although this is a rather difficult problem with a complicated flowfield, comparisons show good agreement with the corresponding experimental data, including the surface heat-transfer rate profile. Therefore, we can say that we have established a numerical method to accurately predict surface heat-transfer in hypersonic shock interacting flows. Finally, detailed analysis of the computed flowfield has been made.